Gasoline dispensing system for airplanes



June 23, 1953 A. E. WATTS, JR., ET AL 2,642,957

GASOLINE DISPENSING SYSTEM FOR AIRPLANES 4 sheets-sh et 1 Filed Aug. 27, 1948 1N VEN TORS A LBER T EWATTS, JR- g? CK R. PARKER ATTORNEY.

June 23, 1953 A. E. wATTs, JR., ET AL 2,642,957

GASOLINE DISPENSING SYSTEM FOR AIRPLANES 4 Sheets-Sheet 2 Filed Aug. 27, 1948 INVENTORS AL BERT E, WATTS,JR. JACK R. PARKER ATTORNEY June 23, 1953 A. E. WATTS, JR, ET AL GASOLINE DISPENSING SYSTEM FOR AIRPLANES Filed Aug. 27, 1948 4 Sheets-Sheet 3 INVENTORS ALBER 7'. E. WA TTSJR. JACK R. PARKER ATTORNEY.

June 23, 1953 A. E WATTS, JR., ET AL 2,542,957

GASOLINE DISPENSING SYSTEM FOR AIRPLANES Filed Aug. 2'7, 1948 4 Sheets-Sheet 4 INVENTORS A LBERT E-WA 773, (JR JA UK R. PARKER ATTORN E.Y

Patented June 23, 1953 UNITED STATES PATENT OFFICE GASOLINE DISPENSING SYSTEM FOR AIRPLANES Albert E. Watts, Jr., Great Neck, and Jack R. Parker, Brooklyn, N. Y., assign'ors to Wattpar Corporation, a corporation of Delawarev Application August 27, 1948, Serial No. 46,398

9 Claims. 1

This invention relates to a fueling and servicing system for airports or lesser landing fields, and more particularly of the type having submerged fuel storage tanks and distributing piping leading to a number of fueling and servicin units disposed relative to the landing strips or loading areas, so that the units are in proper position to fuel and service the plane. When not in use, such fueling and servicing units are contained Within a pit casing submerged in the ground, so that with the cover plate closing the pit, no obstruction appears on the ground.

The chief objects of this invention are concerned with the aforesaid elevatable fueling and servicing unit, and include: An elevatable unit normally contained within the submerged pit casing which has a circular plate covering the pit (when the unit is in lowered position) and provided with a hand hole wherethrough the controls are readily accessible; a unit as described enabling an attendant standing on said circular plate to reach through said handhole to cause the raising of the unit, together with said plate supporting the attendant, to the proper elevation relative to the wing or other part of the serviced airplane; the unit as described in which a plurality of vertical standards extend upwardly from the top of the unit and pass through openings in the circular plate so that as the unit is being raised the said vertical standards maintain the plate and the elevatable unit in positional relationship and form a guard rail about the plate (or unit) Allied objects are: The provision in an elevatable unit as described, of a platform extension movable to a position beyond the elevated unit to bridge across to the wing or other part of an airplane, and retractable within the confines of the elevatable unit; the provision for preventing the lowering of the unit when the platform extension is in its said bridging position; the provision for rotating said unit to an'gularly position its said platform extension relative to an airplane being serviced; the provision of a means for maintaining the pit casing sealed against rain and water in all positions of the cell uni-t, including its elevated position. I

Further objects are: A fueling system for airplanes in which the fuel is pumped under pressure to the elevatable dispensing units by a pump or pumps at the storage tanks, all of which are submerged, there being no fuel pump either in the elevatable unit or in its pit casing; the provision in such a system of a length of flexible hose inthe fuel line to the 'el'evatable unit; the

2 a provision of a hose reel on such unit with a nozzle in a position for ready access through a handhole in the aforesaid pit cover.

For the attainment of the foregoing and such other objects, advantages and features as may appear or be pointed out herein, we have shown a preferred embodiment of our invention in the accompanying drawings, wherein:

Fig. l is a sectional elevation through an improved dispensing unit (on the line i-I of Fig. 2);

Fig. 2 is a cross-sectional view of the unit, taken on the line 2-2 of Fig. 1;

Fig. 3 is another sectional elevation, but taken on the line 3-4 of Fig. 2; i

Fig. 4 is a top View of the unit, looking in the directionof lines 4-4 of Fig. 3;

Fig. 5 is a fragmentary elevational section, on

a the line 5-5 of Fig. 4;

Fig. 6 is a detail of the weatherproof caps for the handrails, being in Section;

Fig. '7 is a top view of the caps (Fig. 6);

Fig. 8 is an elevational view, with the unit in elevated position;

Fig. 9 is a detail view, in section, of the construction of the platform extension;

Fig. 10 is a detail view, partially in section, of the means employed for moving the platform extension;

Fig. 11 is a detail showing the means which prevents the lowering of the unit without first retracting the platform extension;

Fig. 12 is an elevational section, taken on line I2- l2 of Fig. 13, showing the mechanism for rotating the unit;

Fig. 13 is a plan view of the parts of Fig. 12, looking in the direction of line l3-l3 in Fig. 12, but on a somewhat reducedscale;

Fig. 14 is a perspective view of the tank and pumping system and the distribution piping to various dispensing units, and'showing one unit in elevated position and fueling the wing tank of an airplane;

Fig. 15 is a side view of an airplane, with the dispensing unit in position to fuel its wing tank;

Fig. 16 is a plan view, on reduced scale, of two airplanes and a plurality of dispensing units in position relative to the wings thereof, and

Fig. 1'7 is a front view of a dispensing unit, showing its platform extension, lights and register.

The improved system of our invention comprises a plurality of submerged fuel storage tanks 32 (see Fig. 14), each having a submerged pump 29 to pump the fuel through a plurality of distributing pipes 28, each connected to one or more dispensing and servicing units. Only one such unit is shown in Fig. 14 where it is represented by a pit casing 3 which is set into the ground, and the dispensing and servicing unit I which is shown in elevated position in Fig. 14, to fuel the wing tank of an airplane 33.

Said tank pump 29 is disposed in accessible position in a submerged pump pit 66 at each storage tank 32, being shown in Fig. 14 in overlying relation thereof. Each storage pump unit is provided with a check valve H in its distributing pipe 28. From the main distributing line (28) of a storage unit 32-66, e. g. the extreme left one shown in Fig. 14, T-branches are provided for the several dispensing units on that particular line. One such T-branch is shown leading to a submerged valve pit 3| adjacent to the dispensing unit.

The inlet connections to the storage tanks 32 is indicated in Fig. 14, at 69. The vent pipe of these tanks is shown at 68. Additionally, each pump pit 66 has a depth gauge 61 (shown only in connection with the extreme right tank 32).

Referring now to Fig. l, the submerged pit casing 3 of each dispensing and servicing unit has an annular rim l6 flush with the ground (I 4), having an annular rabbet or shoulder to accept a circular plate l5, as clearly shown in Fig. 1. The elevatable dispensing and servicing unit, Fig. l, is generally designated l which reference number points to an enclosed cylindrical cell. Cell unit I is supported by a plurality of telescopic pistons 2 working in their respective cylinders, the elevation or lowering of unit I being controlled by the oil pressure to the piston cylinders (as will be more fully described subsequently) The submerged valve pit 3| described above in connection with the general showing of Fig. 14, appears in Figs. 1 and 2 adjacent the pit casing 3. The aforesaid distributing pipe 28 (from the storage pumps, Fig. 14) is shown in Figs. 1-2 connected through a solenoid operated valve 24 to a short length of pipe 28 to a flexible hose 26 within the pit casing in underlying relation to cell unit I, the flexible hose leading into the bottom of the cell unit, as clearly shown in Fig. 1. Within the cell unit flexible hose 26 connects through a check valve 25, strainer 5 and meter 4 to a hose reel 9. The nozzle of the hose of reel 9 is designated I2; when it is lifted off its hook or seat in which it is normally disposed, a wired connection (not shown) to solenoid valve 24 causes the latter to open and permit the flow of fuel until the nozzle is replaced on its hook, this flow being registered on dial 8 connected to meter 4. Hose reel 9 is implemented with a pulley H] which is belt or otherwise driven from an electric motor H, for winding up the hose after use.

Valve pit 3| also has a motor control 23, Fig. 1, for a sump pump 21 for draining the bottom of pit casing 3, the discharge therefrom being a small pipe I2 leading back to valve pit 3|.

The aforesaid circular plate |5 which, in the normal, lowered position of the elevatable unit, Fig. 1, is flush with casing rim l6 and ground I4, is provided with a plurality of holes l3 wherethrough respective ones of the vertical standards l3 of a guard rail are slideable, as clearly shown in Fig. 1. Vertical standards |3 of the guard rail are secured to the top of the elevatable unit I, and form a partial circular enclosure, see Fig. 4, by a plurality of arcuate hand rail sections 43 which connect to a cap 43 secured at the top of vertical standards l3, see detail, Figs. 6-7. As shown in the latter figures, circular plate I5 is provided with recesses 44 for caps 43, so that when the unit is lowered into the ground, caps 43 completely cover holes |3 in plate I 5, thus making the installation completely rainproof. Additionally, the top surface of plate I 5 has an arcuate groove l5, Fig. 6, for snugly receiving the rail sections 43*. Hence in the normal, lowered position of the unit, cap 43 will be received in recess 44 and rail sections 43 in arcuate grooves l5 so that a flush surface will be presented with no projections which might trip persons on the field.

In operation, the attendant stands on the circular plate l5 (within the area defined by the rail sections 43*, which in the normal, lowered position of the unit, are close to the top surface of plate I5) and, by certain manipulations-soon described-causes the cell unit I to rise. As the cell unit rises, the vertical standards l3 project upwardly, through their said openings in plate I5, thus forming a guard enclosure about the attendant. When the cell, in continuing to rise. or rather its top 4| reaches the underside of circular plate l5, see Fig. 5, the lattertogether with the attendant thereon-is likewise raised by the ascending unit. Shock absorbers 22 are provided on top 4| of the unit to ease the abutting of the cell top 4| and the circular plate I5.

In circular plate I5 is a handhole 42 wherethrough the attendant can reach the controls for elevating the unit, the fuel nozzle |2, etc. Just below opening 42 is a control 38 which is connected by flexible wire 40, Fig. 3, to motor 20 which drives oil pump 2| for operating the elevating-and-lowering pistons 2; the oil reservoir is designated l9 and the oil pressure piping 39. Control 38 may be fitted with a deadmans switch, so that when the operator removes his hand from control 38 the cell will remain at whatever elevation it had been brought when the operators hand is removed.

The other controls are assembled for ready access in a control box 34 on the roof 4| of the unit, easily reached when handhole 42 is opened. Among these is a control 36 for motor for rewinding the fuel hose on reel 9, and a control 31 for resetting the register. These controls enable parts within the cell unit I to be operated from outside of the cell. However, the sides of the cell are removable so that, when the inner parts are to be repaired, the unit is elevated to the desired height from the ground, and the particular side or sides removed to gain ready access to the interior of the unit.

The cell unit I is continued in its ascent by the attendant standing on its circular plate l5, until it is raised to the proper elevation relative to the wing of the airplane, as in Fig. 15. To facilitate the attendants movement between circular plate l5 of the elevated unit and the top of the wing, a platform extension is spanned from the unit to the wing. Normally, platform extension, is contained within cell just below its roof or top 4|, Fig. 1. The construction 01' platform extension I1 is detailed in Figs. 9 and 10, where it will be seen that the platform I! is in the form of an exaggerated I in section; it is slideably mounted on a pair of frame members or tracks 50 which are disposed in the two channels of the I-shape, the platform having a plurality of horizontally-disposed anti-friction rollers 49 between it and the top and bottom surfaces of horizontal tracks 50' and a pluralityof. vertically-disposed anti-friction rollers 49 between its web and the side edges of tracks 50. It will be observed, best from Fig. 4, that the guard rail 43 does not form a complete circle but that a wide portion has no rail; this is omitted so that the attendant may move from the circular plate l to the wing or otherpart of the airplane; also, it will be observed from this figure that the platform-extension I1 is so disposed that it may be moved outwardly at this point (where there is a gap in the guard rail).

For the purpose of extending and retracting platform [1 its underside is provided with rack teeth 5| with which mesh a pinion 52 secured on a spindle 54 from a speed reducer 53 driven by a motor l8. Fig. 10. The control or switch for platform motor I8 is designated 55 in Fig. 2 and is on the aforesaid control box 34. The motor is and reducer 53, Fig. 10, are fitted with reversing mechanism so that the platform extension H can be extended from, or retracted into, the cell unit I at will. The distal end of the platform extension is provided with a rubber v bumper 56 to protect the surface of the airplane wing.

To assure that platform extension 11 has been retracted into cell unit I before the latter descends into pit casing 3, the safety device shown in Fig. 11 is provided. In this figure the circuit to the elevator motor (shown in Fig. 3) is designated 51 and has in one of its lines contacts 51 51 which are connectable by a jumper 58 The latter is disposed at one end of a short spindle 5B slideably mounted in a wall of a housing 60, a compression helical spring 588 between the housing and an enlarged head 58' on the distal end of spindle 58 normally tends to move the spindle outwardly (to the right in Fig. 11) to withdraw jumper 58 and thus open the circuit to the elevator motor. It will be noted from Fig. 11 that said enlarged head 58' of the spindle is abuttable by the rack 5| (or other part) of platform extension [1. In the normal, retracted position of platform extension 11 (to the left i in Fig. 11) spindle 58 is maintained in circuitclosing position, against the opening-urgency of spring 58s. When the platform is projected (to the right), its end leaves the spindle head 58', thus permitting the spring to open the circuit to the elevator motor.

It may be desirable to rotate the unit to facilitate the positioning or spanning of the platform extension between the unit and the wing of the airplane. For this purpose a ring 6|, Figs. 12-13, having internal teeth is secured to the underside of cell unit I, with which mesh a pinion 65 secured at one end of a spindle 64 driven through a speed reducer, from motor 63. Anti-friction bearings 52 are provided for mounting cell unit I for rotation. The control for motor 53 may be located in the aforesaid control box, to enable the unit to be turned in either direction.

Cell unit I, Fig. 1, may be provided with CO2 tanks 6 and hose reel 1. The outside of the cell unit I, Fig. 17, is provided with a flood light 30, and also with a gasoline consumption dial 8. The unit may be provided with other accessories, such as a defueling system, battery-charging system, air-conditioning blowers and fans for readying planes before take-off.

A plurality of bars 45, Fig. 8, are spaced about cell unit I and secured at their upper ends to the underside thereof; the lower ends of suspension bars 45 are secured to a circular plate 4B,-tothe outer circumference of which is :attached a strip 41 of neoprene or other suitable material. Suspension bars 45 are sufficiently long so that in. the extreme elevated position of.'the unit, annular strip 41 will still be in engagement with the interior wall of pit casing 3, to serve, together with plate 45, as a Water seal to permit rain or other. liquid from entering the pit casing when the unit is in elevated position, as it is in Fig. 8.

We claim:

1. In a fueling and servicing system for airplanes, in combination, a submerged pit casing, a cylindrical cell unit mounted for vertical move.- ment within said .pit casing and having a plurality ofIvertical standards extending upwardly from the roof thereof, means including a control within said unit for raising the said cylindrical cell unit to an elevated position outside and above the pit casing and for lowering the same to a position entirely within the casing, a circular plate for closing the submerged pit casing when said cylindrical cell unit is in its said lowered position, provided with openings for slideably engaging said vertical standards and with a handhole for gaining access to said elevator controls whereby an attendant on said plate can cause the elevation of said cylindrical cell unit together with the circular plate and himself, said vertical standards guiding the initial movement of the cell relative to the plate and holding the plate on the cell during the final combined elevation of the two.

2. The combination according to claim 1 wherein said vertical standards are provided at their upper ends with arcuate sections to form a guard rail substantially encircling said circular plate when the said cylindrical cell unit is elevated.

3. The combination according to claim 2 wherein the upper surface of the circular plate is provided with an annular groove for receiving said arcuate sections of the guard rail, so that no part thereof projects above the circular plate in the said lowered position of the cylindrical cell unit.

4. The combination according to claim 1 wherein said vertical standards are provided at their upper ends with enlarged caps, and the upper surface of the circular plate is provided with a recess for said cap, so that a waterproof seal is provided for said openings in the circular plate.

5. In a fueling and servicing system for airplanes, in combination, a submerged pit casing, a cell unit mounted for vertical movement from a lowered position within the pit casing to an elevated position outside and above the submerged pit casing, a plate for closing the pit casing when said unit is in its said lowered position, and an electrically controlled platform extension having an exaggerated I shaped cross section with a pair of opposed tracks disposed in the two channels of said I-shaped platform extension, said platform extension mounted on said cell unit for lateral projecting movement relative to the unit and for retractive movement within the unit.

6. The combination according to claim 5 further provided with mechanism for raising and lowering said cell unit, and means for making said mechanism inoperative when the platform extension is in said laterally projected position.

7. The, combination according to claim 6 wherein said raising-and-lowering mechanism includes an electrical circuit provided with an open contact, and said means includes a jumper for closing said contact normally spring urged to circuit-.

opening position, and an element, abuttable by the platform extension when in said retracted position, for moving the jumper to circuit-closing position." a.

8. The combination according to claim 5 provided with means including a motor, speed reducer and a rack and pinion connection for moving the platform extension to its said laterally projected position'and toits said retracted position. a l

9. The combination according to claim 5 further provided with means including a motor, speed reducer and an internal gear and pinion for rotating said cell unit to angularly position said laterally projecting platform extension.

ALBERT E. WA'I'IS, JR. JACK R. PARKER.

8 References Cited in the file of this patent UNITED STATES PATENTS Number Name Date Fleming Apr. 2, 1907 Hillman Oct. 23, 1917 Sago Mar. 31, 1925 Stukenborg July 19, 1932 Tamini May 29, 1934 Clark Jan. 1, 1935 Watts et a1 Jan. 20, 1948 

